CN209724495U - A kind of supporting structure of micro-gas-turbine machine rotor - Google Patents
A kind of supporting structure of micro-gas-turbine machine rotor Download PDFInfo
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- CN209724495U CN209724495U CN201920371956.0U CN201920371956U CN209724495U CN 209724495 U CN209724495 U CN 209724495U CN 201920371956 U CN201920371956 U CN 201920371956U CN 209724495 U CN209724495 U CN 209724495U
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Abstract
The utility model discloses a kind of supporting structures of micro-gas-turbine machine rotor, including static pressure radial gas bearing, static pressure radial thrust joint gas bearing, bleed air line and supply air line, static pressure radial gas bearing is mounted remotely from main shaft one end of compressor impeller, and static pressure radial thrust joint gas bearing is arranged close to the main shaft other end of compressor impeller；A channel is opened up between the diffuser and blower casing body of compressor, channel is connected to by bleed air line with supply air line, supply air line is arranged in gas turbine housing, and supply air line one end extends to static pressure radial gas bearing, the other end of supply air line extends to static pressure radial thrust joint gas bearing.By the technical solution of the utility model, the revolving speed of miniature gas turbine can be greatly improved, while guaranteeing reliability, complicated air feed equipment needed for hydrostatic gas-lubricated bearing is in turn avoided, significantly simplifies miniature gas turbine structure.
Description
Technical field
The utility model relates to micro gas turbine engine technical field, more particularly to a kind of miniature gas
The supporting structure of turbine wheel.
Background technique
Micro gas turbine engine mainly includes compressor, combustion chamber and turbine, and compressor sucks sky from atmosphere
Gas simultaneously compresses air, and compressed air enters combustion chamber and generates high-temperature fuel gas with fuel mixing after-combustion, and then high temperature fires
Gas flows into expansion work in turbine, and the gas emission after finally pushing turbine acting is to regenerator, after compressing compressor
The combustion gas that is discharged with turbine of air exchange heat.Micro gas turbine engine is with light-weight, power is big, thrust ratio is high
The advantages that, compared with conventional engine, due to minute vehicle have size is small, revolving speed is high, number of components is few, longevity of service,
Thrust is easily adjusted, infra-red radiation is low, the advantages that capable of reusing, in unmanned battle aircraft, antiaircraft weapon target, accurately beat
It hits on the equipments such as ammunition, test vehicle and widely applies, either in military field still in civil field, it, which has, is extremely lured
The application prospect of people.
But each state is all designed micro gas turbine engine and studies stepping up at present, and micro-gas-turbine
For machine while revolving speed is continuously improved, frictional heating phenomenon also can be extremely serious, and the lubricant grease as conventional bearings usually can
Occur rotten and cause bearing unstability, in addition, conventional lubricating system needs complicated oil feed line etc., considerably increases miniature
The complex degree of structure of gas turbine, and this theory is runed counter to " miniature ".
Therefore it provides a kind of supporting structure of the micro-gas-turbine machine rotor of efficient stable, had both been able to satisfy in fact existing higher
The demand of revolving speed, but can greatly realize gas-turbine plant size, " micromation " of weight be those skilled in the art urgently
Problem to be solved.
Utility model content
In view of this, the present invention provides a kind of supporting structures of micro-gas-turbine machine rotor, can greatly improve
The revolving speed of miniature gas turbine, while guaranteeing reliability, complicated air feed equipment needed for hydrostatic gas-lubricated bearing is in turn avoided,
Significantly simplify miniature gas turbine structure.
To achieve the goals above, the utility model adopts the following technical solution:
A kind of supporting structure of micro-gas-turbine machine rotor, including starting motor, compressor and turbine, the starting electricity
Machine, the compressor and the turbine are connected as one by same root main shaft；It is described starting motor motor housing with into
Feed channel contact, the admission line are fixed on admission line shell, and the admission line shell and gas turbine housing are solid
Fixed connection, is supported between the motor housing and the admission line shell by supporting plate；The open end of the compressor and ring
Shape combustion chamber, the toroidal combustion chamber are connected to turbine, and the turbine is connected to regenerator, the toroidal combustion chamber
It is fixed in the cavity of the regenerator, further includes static pressure radial gas bearing, static pressure radial thrust joint gas bearing, bleed
Pipeline and supply air line, the static pressure radial gas bearing are mounted remotely from described main shaft one end of the compressor impeller, institute
State the main shaft other end that static pressure radial thrust joint gas bearing is arranged close to the compressor impeller；The compressor
Diffuser and blower casing body between open up a channel, the channel passes through the bleed air line and the supply air line
Connection, the supply air line is arranged in the gas turbine housing, and described supply air line one end extends to the static pressure radial
Gas bearing, the other end of the supply air line extend to the static pressure radial thrust joint gas bearing.
Further, 8 throttle orifices are offered in the static pressure radial gas bearing, and 8 throttle orifices are along institute
The circumferential direction for stating static pressure radial gas bearing is equidistantly spaced from；One layer is equipped between the static pressure radial gas bearing and the main shaft
Graphite.
Further, the static pressure radial thrust joint gas bearing includes radial support portion and push stopping part, the radial direction
Support portion is arranged vertically with the push stopping part, and the side of the push stopping part is equipped with thrust button；The radial support portion and it is described only
Throttle orifice is offered on pushed section, between the radial support portion and the main shaft and the push stopping part and the thrust button
Between be equipped with one layer of graphite.
Further, the throttle orifice includes air inlet, throttling pore and air cavity, and the air inlet is small by the throttling
Hole is connected to the air cavity, the air cavity and the graphite contact.
By taking above scheme, the beneficial effects of the utility model are:
1) lubrication and support are provided by static pressure radial gas bearing, the operation of miniature gas turbine can be significantly increased
Revolving speed, meanwhile, number of bearings needed for equipment can be reduced using pressurized air radical-thrust joint bearing, be further simplified knot
Structure, and utilizing the centrifugal compressor of miniature gas turbine is static pressure radial gas bearing and pressurized air radical-thrust joint bearing
Gas supply, and can farthest avoid making miniature gas turbine as far as possible using drawback brought by hydrostatic bearing form
" micromation "；
2) static pressure radial gas bearing is immixture form bearing, offers throttle orifice on it, and is applied at bearing shell
One layer of graphite, outside gas supply flows into gap via orifice restriction, using porous restriction, therefore has orifice restriction and Porous
The immixture of throttling；
3) static pressure radial thrust joint gas bearing is immixture form bearing, and have provide simultaneously axial support and
The function of radial support offers throttle orifice in radial support portion and push stopping part, and in radial section bearing shell, thrust section thrust plate
Place is coated with one layer of graphite, and external air source flows into gap after orifice restriction and porous restriction again, have orifice restriction with
The immixture of porous restriction；
4) graphite can either play the role of porous restriction, improve the stability of rotor operation, and can pass through self-lubricating
Effect provides effectively support in low pressure gas supply, can make miniature gas turbine trouble-free operation under entire operating condition.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is the embodiments of the present invention, for those of ordinary skill in the art, without creative efforts, also
Other attached drawings can be obtained according to the attached drawing of offer.
Fig. 1 attached drawing is a kind of overall structure signal of supporting structure of micro-gas-turbine machine rotor provided by the utility model
Figure；
Fig. 2 attached drawing is the structural schematic diagram of static pressure radial gas bearing provided by the utility model；
Fig. 3 attached drawing is the cross-sectional view of Section A-A in Fig. 2；
Fig. 4 attached drawing is the structural schematic diagram that gas bearing is combined in static pressure radial thrust provided by the utility model.
In figure: 1- supporting plate, 2- supply air line, 3- admission line shell, 4- admission line, 5- motor housing, 6- starting electricity
Machine, 7- main shaft, 8- gas turbine housing, 9- bleed air line, 10- regenerator, 11- shell cavity capacity, 12- cavity, 13- annular firing
Room, 14- static pressure radial gas bearing, 15- static pressure radial thrust joint gas bearing, 16- thrust button, 17- blower casing body,
18- compressor, 19- turbine, 20- air inlet, 21- throttling pore, 22- air cavity, 23- graphite, 151- radial support portion, 152-
Push stopping part.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
As shown in Figs 1-4, the utility model embodiment discloses a kind of supporting structure of micro-gas-turbine machine rotor, including
Start motor 6, compressor 18 and turbine 19, starting motor 6, compressor 18 and turbine 19 are connected by same root main shaft 7
It is integrated；The motor housing 5 of starting motor 6 is contacted with admission line 4, and admission line 4 is fixed on admission line shell 3, into
Feed channel shell 3 is fixedly connected with gas turbine housing 8, is supported between motor housing 5 and admission line shell 3 by supporting plate 1；
The open end of compressor 18 is connected to toroidal combustion chamber 13, and toroidal combustion chamber 13 is connected to turbine 19, turbine 19 and backheat
Device 10 is connected to, and it further includes static pressure radial gas bearing 14, static pressure diameter that toroidal combustion chamber 13, which is fixed in the cavity 12 of regenerator 10,
Compressor is mounted remotely to thrust joint gas bearing 15, bleed air line 9 and supply air line 2, static pressure radial gas bearing 14
7 one end of main shaft of 18 impellers, the main shaft 7 that static pressure radial thrust joint gas bearing 15 is arranged close to 18 impeller of compressor are another
End；A channel is opened up between the diffuser and blower casing body 17 of compressor 18, channel passes through bleed air line 9 and air supply pipe
Road 2 is connected to, and supply air line 2 is arranged in gas turbine housing 8, and 2 one end of supply air line extends to static pressure radial gas bearing 14,
The other end of supply air line 2 extends to static pressure radial thrust joint gas bearing 15.The utility model is by using a static pressure
Radial gas bearing provided 14 and static pressure radial thrust joint gas bearing 15 be that miniature gas turbine provides lubrication and supports, and
Using compressor 18 as external feeder, i.e., channel is reserved in the diffuser rear end of compressor 18, and expand in compressor 18
A bleed air line 9 is arranged between depressor and blower casing body 17, the high pressure gas in channel after the extraction of bleed air line 9,
Separately flow into static pressure radial gas bearing 14 and static pressure radial thrust joint gas bearing 15 is realized miniature with providing support
Gas engine being capable of stable operation at higher rotational speeds.
Specifically, offering 8 throttle orifices in static pressure radial gas bearing 14, and 8 throttle orifices are along static pressure radial gas
The circumferential direction of body bearing 14 is equidistantly spaced from；One layer of graphite 23 is equipped between static pressure radial gas bearing 14 and main shaft 7.
Specifically, static pressure radial thrust joint gas bearing 15 includes radial support portion 151 and push stopping part 152, radial branch
Support part 151 is arranged vertically with push stopping part 152, and the side of push stopping part 152 is equipped with thrust button 16；Radial support portion 151 and push stopping part
Throttle orifice is offered on 152, is all provided between radial support portion 151 and main shaft 7 and between push stopping part 152 and thrust button 16
There is one layer of graphite 23.
Specifically, throttle orifice includes air inlet 20, throttling pore 21 and air cavity 22, air inlet 20 by throttling pore 21 with
Air cavity 22 is connected to, and air cavity 22 is contacted with graphite 23.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments can be realized professional and technical personnel in the field or using originally practical new
Type.Various modifications to these embodiments will be readily apparent to those skilled in the art, and determine herein
The General Principle of justice can be realized in other embodiments without departing from the spirit or scope of the present utility model.Cause
This, the present invention will not be limited to the embodiments shown herein, and is to fit to and principles disclosed herein
The widest scope consistent with features of novelty.
Claims (4)
1. a kind of supporting structure of micro-gas-turbine machine rotor, including starting motor (6), compressor (18) and turbine (19),
The starting motor (6), the compressor (18) and the turbine (19) are connected as one by same root main shaft (7)；Institute
The motor housing (5) for stating starting motor (6) is contacted with admission line (4), and the admission line (4) is fixed on admission line shell
(3) on, the admission line shell (3) is fixedly connected with gas turbine housing (8), the motor housing (5) and the air inlet
It is supported between pipeline shell (3) by supporting plate (1)；The open end of the compressor (18) is connected to toroidal combustion chamber (13), institute
It states toroidal combustion chamber (13) to be connected to turbine (19), the turbine (19) is connected to regenerator (10), the annular firing
Room (13) is fixed in the cavities (12) of the regenerator (10), which is characterized in that further include static pressure radial gas bearing (14),
Gas bearing (15), bleed air line (9) and supply air line (2), the static pressure radial gas bearing are combined in static pressure radial thrust
(14) it is mounted remotely from the main shaft (7) one end of the compressor (18) impeller, gas axis is combined in the static pressure radial thrust
Hold the main shaft (7) other end that (15) are arranged close to the compressor (18) impeller；The diffuser of the compressor (18)
A channel is opened up between blower casing body (17), the channel passes through the bleed air line (9) and the supply air line
(2) it is connected to, the supply air line (2) is arranged in the gas turbine housing (8), and the supply air line (2) one end extends to
The static pressure radial gas bearing (14), the other end of the supply air line (2) extend to the static pressure radial thrust joint gas
Body bearing (15).
2. a kind of supporting structure of micro-gas-turbine machine rotor according to claim 1, which is characterized in that the static pressure diameter
8 throttle orifices are offered on gas bearing (14), and 8 throttle orifices are along the static pressure radial gas bearing (14)
Circumferentially it is equidistantly spaced from；One layer of graphite (23) is equipped between the static pressure radial gas bearing (14) and the main shaft (7).
3. a kind of supporting structure of micro-gas-turbine machine rotor according to claim 1, which is characterized in that the static pressure diameter
Include radial support portion (151) and push stopping part (152) to thrust joint gas bearing (15), the radial support portion (151) and
The push stopping part (152) is arranged vertically, and the side of the push stopping part (152) is equipped with thrust button (16)；The radial support portion
(151) and in the push stopping part (152) throttle orifice is offered, between the radial support portion (151) and the main shaft (7),
And one layer of graphite (23) is equipped between the push stopping part (152) and the thrust button (16).
4. according to a kind of described in any item supporting structures of micro-gas-turbine machine rotor of Claims 2 or 3, which is characterized in that
The throttle orifice includes air inlet (20), throttling pore (21) and air cavity (22), and the air inlet (20) is small by the throttling
Hole (21) is connected to the air cavity (22), and the air cavity (22) contacts with the graphite (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920371956.0U CN209724495U (en) | 2019-03-22 | 2019-03-22 | A kind of supporting structure of micro-gas-turbine machine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920371956.0U CN209724495U (en) | 2019-03-22 | 2019-03-22 | A kind of supporting structure of micro-gas-turbine machine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209724495U true CN209724495U (en) | 2019-12-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920371956.0U Active CN209724495U (en) | 2019-03-22 | 2019-03-22 | A kind of supporting structure of micro-gas-turbine machine rotor |
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| CN (1) | CN209724495U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360576A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Integrated impeller side-mounted thermoelectric conversion system rotating shaft structure |
| CN112664470A (en) * | 2020-12-24 | 2021-04-16 | 北京理工大学 | High-speed air compressor convenient to heat dissipation |
-
2019
- 2019-03-22 CN CN201920371956.0U patent/CN209724495U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360576A (en) * | 2020-10-26 | 2021-02-12 | 北京动力机械研究所 | Integrated impeller side-mounted thermoelectric conversion system rotating shaft structure |
| CN112664470A (en) * | 2020-12-24 | 2021-04-16 | 北京理工大学 | High-speed air compressor convenient to heat dissipation |
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